EP1031637A1 - Superalliage à base de nickel - Google Patents

Superalliage à base de nickel Download PDF

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Publication number
EP1031637A1
EP1031637A1 EP00301002A EP00301002A EP1031637A1 EP 1031637 A1 EP1031637 A1 EP 1031637A1 EP 00301002 A EP00301002 A EP 00301002A EP 00301002 A EP00301002 A EP 00301002A EP 1031637 A1 EP1031637 A1 EP 1031637A1
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EP
European Patent Office
Prior art keywords
single crystal
100ppm
nickel based
superalloy
rhenium
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EP00301002A
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German (de)
English (en)
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EP1031637B1 (fr
Inventor
Robert Walter Broomfield
Colin Neil Jones
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Rolls Royce PLC
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Rolls Royce PLC
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y10T428/12611—Oxide-containing component
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12861—Group VIII or IB metal-base component
    • Y10T428/12944—Ni-base component

Definitions

  • the present invention relates to nickel based superalloys, particularly to nickel based single crystal superalloys, or particularly nickel based single crystal superalloys for use as turbine blades, turbine vanes, turbine seals and combustor components of gas turbine engines, but they may be used in internal combustion engines etc.
  • Nickel based single crystal superalloys have been developed to provide improved high temperature mechanical properties such as creep strength.
  • Other important properties which need to be optimised are density, resistance to oxidation, resistance to corrosion, compatibility with protective coatings, heat treatment response and castability.
  • the first generation of nickel based single crystal superalloys contained no rhenium, examples of these are disclosed in published UK patent application nos. GB2039296A, GB2073774A, GB2105369A, GB2106138A and GB2151659A.
  • the first generation of nickel based single crystal superalloys have densities of 7.9 to 8.7 gm per cm 3 .
  • the second generation of nickel based single crystal superalloys contained about 3wt% rhenium, examples of these are disclosed in published European patent application nos. EP0155827A and EP0208645A.
  • the second generation of nickel based single crystal superalloys have densities of 8.7 to 8.9 gm per cm 3 .
  • the second generation of nickel based single crystal superalloys have a benefit in creep strength capability of about 30°C over the first generation of nickel based single crystal superalloys.
  • the third generation of nickel based single crystal superalloys contained about 6wt% rhenium, examples of these are disclosed in US patents US5366695 and US5270123 and published European patent application no. EP0848071A.
  • the third generation of nickel based single crystal superalloys have densities of 8.9 to 9.1 gm per cm 3 .
  • the third generation of nickel based single crystal superalloys have a benefit in creep strength capability of about 30°C over the second generation of nickel based single crystal superalloys.
  • the turbine blades requiring the greatest creep strength are usually those in the first stage of uncooled turbine blades, and for these turbine blades a third generation nickel based single crystal superalloy is used. However, for turbine blades and turbine vanes which are cooled the requirements are different. The creep strength requirement is lower and hence creep properties similar to the second generation nickel based single crystal superalloy are sufficient. It is often the case that these cooled turbine blades and turbine vanes are protected by a ceramic thermal barrier coating. A major concern with a ceramic thermal barrier coating is that the ceramic thermal barrier coating will spall prematurely during engine service. The adherence of a ceramic thermal barrier coating is influenced by many factors, but a major factor is the composition of the superalloy substrate on which the ceramic thermal barrier coating is deposited.
  • the present invention seeks to provide a novel nickel based single crystal superalloy which has creep properties and high temperature oxidation resistance similar to a second generation nickel based single crystal superalloy but has reduced density compared to a second generation nickel based single crystal superalloy and better compatibility with a ceramic thermal barrier coating than a second generation nickel based single crystal superalloy.
  • the present invention provides a nickel based single crystal superalloy comprising 3-11wt% cobalt, 4.7-5.7wt% chromium, 2.4-3.0wt% molybdenum, 3.0-3.8wt% tungsten, 3.0-3.8wt% rhenium, 5.5-7.0wt% aluminium, 5.0-6.0wt% tantalum, 0.5-1.0wt% niobium, 0-0.2wt% hafnium, 0-150ppm carbon, 0-100ppm yttrium, 0-100ppm lanthanum, 0-5ppm sulphur and the balance nickel plus incidental impurities.
  • the nickel based single crystal superalloy may comprise 9-11wt% cobalt, 5.1-5.4wt% chromium, 2.6-2.9wt% molybdenum, 3.2-3.5wt% tungsten, 3.2-3.5wt% rhenium, 6.05-6.3wt% aluminium, 5.4-5.7wt% tantalum, 0.7-0.9wt% niobium, 0.07-0.12wt% hafnium, 50-150ppm carbon, 0-100ppm yttrium, 0-100ppm lanthanum, 0-5ppm sulphur and the balance nickel plus incidental impurities.
  • the nickel based single crystal superalloy comprises 3-5wt% cobalt, 5.1-5.4wt% chromium, 2.6-2.9wt% molybdenum, 3.2-3.5wt% tungsten, 3.2-3.5wt% rhenium, 6.05-6.3wt% aluminium, 5.4-5.7wt% tantalum, 0.7-0.9wt% niobium, 0.07-0.12wt% hafnium, 50-150ppm carbon, 0-100ppm yttrium, 0-100ppm lanthanum, 0-5ppm sulphur and the balance nickel plus incidental impurities.
  • the nickel based single crystal superalloy may comprise 4wt% cobalt, 5.2wt% chromium, 2.7wt% molybdenum, 3.35wt% tungsten, 3.4wt% rhenium, 6.2wt% aluminium, 5.5wt% tantalum, 0.8wt% niobium, 0.1wt% hafnium, 0-100ppm yttrium, 0-100ppm lanthanum, 0-5ppm sulphur and the balance nickel plus incidental impurities.
  • the nickel based single crystal superalloy may comprise 10wt% cobalt, 5.2wt% chromium, 2.7wt% molybdenum, 3.35wt% tungsten, 3.4wt% rhenium, 6.2wt% aluminium, 5.5wt% tantalum, 0.8wt% niobium, 0.1wt% hafnium, 100ppm carbon, 0-100ppm yttrium, 0-100ppm lanthanum, 0-5ppm sulphur and the balance nickel plus incidental impurities.
  • the present invention also provides a cast single crystal nickel based superalloy article, the superalloy of the article comprising 3-11wt% cobalt, 4.7-5.7wt% chromium, 2.4-3.0wt% molybdenum, 3.0-3.8wt% tungsten, 3.0-3.8wt% rhenium, 5.5-7.0wt% aluminium, 5.0-6.0wt% tantalum, 0.5-1.0wt% niobium, 0-0.2wt% hafnium, 0-150ppm carbon, 0-100ppm yttrium, 0-100ppm lanthanum, 0-5ppm sulphur and the balance nickel plus incidental impurities.
  • the cast single crystal nickel based superalloy article may comprise 9-11wt% cobalt, 5.1-5.4wt% chromium, 2.6-2.9wt% molybdenum, 3.2-3.5wt% tungsten, 3.2-3.5wt% rhenium, 6.05-6.3wt% aluminium, 5.4-5.7wt% tantalum, 0.7-0.9wt% niobium, 0.07-0.12wt% hafnium, 50-150ppm carbon, 0-100ppm yttrium, 0-100ppm lanthanum, 0-5ppm sulphur and the balance nickel plus incidental impurities.
  • the cast single crystal nickel based superalloy article comprises 3-5wt% cobalt, 5.1-5.4wt% chromium, 2.6-2.9wt% molybdenum, 3.2-3.5wt% tungsten, 3.2-3.5wt% rhenium, 6.05-6.3wt% aluminium, 5.4-5.7wt% tantalum, 0.7-0.9wt% niobium, 0.07-0.12wt% hafnium, 50-150ppm carbon, 0-100ppm yttrium, 0-100ppm lanthanum, 0-5ppm sulphur and the balance nickel plus incidental impurities.
  • the cast single crystal nickel based superalloy article may comprise 4wt% cobalt, 5.2wt% chromium, 2.7wt% molybdenum, 3.35wt% tungsten, 3.4wt% rhenium, 6.2wt% aluminium, 5.5wt% tantalum, 0.8wt% niobium, 0.1wt% hafnium, 0-100ppm yttrium, 0-100ppm lanthanum, 0-5ppm sulphur and the balance nickel plus incidental impurities.
  • the cast single crystal nickel based superalloy article may comprise 10wt% cobalt, 5.2wt% chromium, 2.7wt% molybdenum, 3.35wt% tungsten, 3.4wt% rhenium, 6.2wt% aluminium, 5.5wt% tantalum, 0.8wt% niobium, 0.1wt% hafnium, 100ppm carbon, 0-100ppm yttrium, 0-100ppm lanthanum, 0-5ppm sulphur and the balance nickel plus incidental impurities.
  • the cast single crystal nickel based superalloy article may comprise a turbine blade, a turbine vane or a combustor component.
  • the cast single crystal nickel based superalloy article may comprise at least one internal passage for the flow of cooling fluid.
  • the cast single crystal nickel based superalloy article may comprise a bond coating on the article and a ceramic thermal barrier coating on the bond coating.
  • the bond coating may comprise a layer of alumina.
  • the bond coating may comprise a layer comprising platinum enriched gamma prime phase and platinum enriched gamma phase.
  • the rhenium level was set to at least 3wt%.
  • Table 1 A number of alloys were prepared as shown in Table 1, and Table 1 also includes known superalloys CMSX4 and CMSX10 of Cannon-Muskegon Corporation, of 2875 Lincoln Street, Muskegon, Michigan, USA and described in European patent application EP0155827A and US patent US5366695 respectively.
  • Superalloys 2071-2083 are not within the scope of the present invention whereas superalloys 2084-2087 are within the scope of the present invention.
  • superalloys 2074-2079 are a family based on superalloy 2072 and that superalloys 2080-2084 are a family and that superalloys 2085-2087 are a family based on superalloy 2084.
  • Elements (wt%) Alloy Co Cr Mo W Re Al Ti Ta Nb Hf Ni CMSX4 9.5 6.5 0.6 6.4 3.0 5.6 1.0 6.5 0 0.1 Bal. CMSX10 2.7 2.0 0.4 5.3 6.3 5.65 0.2 5.8 7.9 0.04 Bal. 2071 9.5 6.6 4.5 0 2.8 5.6 1.3 7.3 0.3 0.1 Bal. 2072 4.0 6.0 3.3 1.9 3.0 6.2 0.4 5.95 0.8 0.1 Bal.
  • the superalloys in Table 1 were initially tested for compatibility with a known thermal barrier coating system by depositing about 8 ⁇ m of platinum onto the samples of the superalloy substrate and heat treating at 1150°C to form a layer comprising platinum enriched gamma phase and platinum enriched gamma prime phase. This layer together with a layer of alumina which forms on the layer becomes a bond coating for a ceramic thermal barrier coating deposited by electron beam physical vapour deposition.
  • the samples of the superalloys with the bond coatings and ceramic thermal barrier coatings were isothermally soaked for 25 hours at specific temperatures, and the temperature at which the ceramic thermal barrier coating spalled was noted and the highest temperature at which the ceramic thermal barrier coating did not spall was noted.
  • the temperature above which the ceramic thermal barrier coating spalls is a measure of the compatibility between the superalloy substrate and the ceramic thermal barrier coating.
  • the levels of sulphur and titanium and the highest temperature at which the ceramic thermal barrier coating did not spall are shown in Table 2.
  • High levels of rhenium in the superalloy are beneficial for compatibility with the ceramic thermal barrier coating, see for example CMSX10 which has 6.2wt% rhenium loses it's ceramic thermal barrier coating above 1250°C and superalloy 2084 which has 3.4wt% rhenium loses it's ceramic thermal barrier coating above 1230°C is much better than superalloys 2080 to 2083 which have 3.0wt% rhenium and which lose their ceramic thermal barrier coatings above 1210°C.
  • Low, preferably zero, levels of titanium in the superalloy are beneficial for compatibility with the ceramic thermal barrier coating, see for example CMSX10 which has 0.20wt% titanium and superalloy 2079 and 2084 which have zero titanium lose their ceramic thermal barrier coatings above 1230°C and CMSX4 which has 1.0wt% titanium and low sulphur level loses it's ceramic thermal barrier coating above 1190°C.
  • Low levels of cobalt are beneficial for compatibility with the ceramic thermal barrier coating, see for example the alloy sequence 2084, 2085 and 2086, in which the alloys have the same composition apart from a progressive increase in cobalt level from 4wt% to 10wt%. The spallation temperature decreased progressively from 1230°C to 1190°C in that sequence.
  • the superalloy should have as low a level of sulphur as possible, preferably less than 5ppm, preferably zero, but his depends on the purity of the raw materials.
  • the superalloy should have zero titanium.
  • the superalloy should have as high a rhenium level as possible, but this is limited by the density and cost requirements.
  • the superalloy should have a low cobalt level, around 4wt%, unless the requirement for metallurgical stability is paramount, in which case a high cobalt level, around 10wt%, is preferred.
  • the level of tungsten is reduced and the level of molybdenum is increased, the level of tantalum is reduced and the level of niobium is increased and the level of titanium is reduced to zero and the level of aluminium is increased as seen in Table 1.
  • the requirement for high temperature oxidation resistance is essentially the same as the requirement for compatibility with ceramic thermal barrier coatings, but with a requirement for high levels of aluminium. Additionally yttrium and/or lanthanum may be added at a up to 100 parts per million to improve oxidation resistance.
  • the creep strength in the temperature range 850°C-1050°C is controlled by the composition of the gamma phase, the width of the gamma phase channels between the gamma prime phase particles, the gamma phase/gamma prime phase mismatch and the strength of the gamma prime phase.
  • the gamma phase/gamma prime phase mismatch is already fixed and the gamma phase channel width is controlled by the volume fraction of gamma prime phase, aiming to be about 65%.
  • chromium has the detrimental effect of promoting the formation of the sigma phase, however slightly lower chromium levels may be tolerated if the rhenium level is higher. Hence the rhenium level is increased to about 3.4wt%.
  • Freckles are small chains of equiaxed grains that form during the solidification of the single crystal superalloy. Freckles form because of differences in density between the solid and liquid phases in the mushy zone, the density gradient produces currents in the liquid phase which break off pieces of dendrite. The pieces of dendrite promote the nucleation of separate grains. Freckling is controlled by having sufficient heavy gamma prime phase forming elements such as tantalum to balance the heavy gamma phase forming elements such as tungsten and rhenium.
  • a simple empirical formula to avoid freckling is:- Ta / W+Re is greater than or equal to 0.8
  • a more complex empirical formula to avoid freckling is defined in published International patent application No W097/48827A:- Ta+(1.5xHf)+(0.5xMo)-(0.5xTi) / W+(1.2xRe) is greater than 0.7, pref 1.0
  • the above two formulas use wt%.
  • the superalloys of the present invention have a parameter of 0.95 for the latter formula and this should give little freckling.
  • Oxide inclusions may promote the formation of defects in single crystal superalloy castings.
  • the requirement for alloy cleanliness is achieved by adding carbon because it is known that carbon reduces the level of deleterious oxides inclusions in the single crystal superalloy.
  • the carbon may also provide some grain boundary strength. However, too much carbon promotes script carbides which reduce the fatigue strength of the superalloy. Therefore carbon up to 150ppm, preferably 100ppm, may be added to clean the superalloy without any significant effect on the fatigue strength.
  • Cyclic oxidation testing has been performed on a burner rig, the cycling rate was 4 cycles per hour and 0.25 ppm of simulated sea salt was added to the gas flow to simulate operation in a marine environment.
  • the measure of the amount of attack on the superalloy is by metal loss per surface and the data is shown in figure 1 for testing at a temperature of 1100°C for superalloys 2073, 2080-2084, 2086 and CMSX4. It can be seen that superalloys 2080-2084 and 2086have similar oxidation resistance to CMSX4. In fact the preferred superalloy 2086 has the best oxidation resistance of the series.
  • the creep performance can be expressed as the time to 1% creep strain under various conditions of stress and temperature. These times for the superalloys 2084 and 2086 are listed in Table 3, and a comparison is made with the creep properties of CMSX4 in figure 2.
  • the vertical axis of this graph is the ratio of creep lives between superalloys 2084 or 2086 of the present invention and CMSX4.
  • the general trend is for the superalloys of the present invention to be worse than CMSX4 at temperatures below 850°C, and equivalent to CMSX4 at temperatures above 850°C up to 1100°C, the highest temperature at which tests were performed.
  • the main advantage of the nickel based single crystal superalloys according to the present invention compared to current second generation nickel based single crystal superalloys is that the superalloys of the present invention have improved compatibility with ceramic thermal barrier coatings such that the bond coating temperature may be increased by 20°C-40°C for a given life.
  • Another advantage of the nickel based single crystal superalloys according to the present invention compared to current second generation nickel based single crystal superalloys is that the superalloys of the present invention have lower density reducing the weight of the component, turbine blade or turbine vane, with consequential reduction in weight of the turbine disc.
  • nickel based single crystal superalloys according to the present invention compared to current second generation nickel based single crystal superalloys is that the superalloys of the present invention have improved resistance to freckling and to the formation of stray grains, this enables thicker sections to be cast successfully. Additionally the nickel based single crystal superalloys according to the present invention have similar high temperature high temperature oxidation resistance and creep strength compared to current second generation nickel based single crystal superalloys.
  • the ceramic thermal barrier coating may be deposited by other suitable methods for example sputtering, vacuum plasma spraying, air plasma spraying, chemical vapour deposition etc.
  • the ceramic thermal barrier coating may comprise yttria stabilised zirconia, magnesia stabilised zirconia, ceria stabilised zirconia or other suitable ceramics.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Crystals, And After-Treatments Of Crystals (AREA)
EP00301002A 1999-02-22 2000-02-09 Superalliage à base de nickel Expired - Lifetime EP1031637B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GBGB9903988.5A GB9903988D0 (en) 1999-02-22 1999-02-22 A nickel based superalloy
GB9903988 1999-02-22

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EP1031637A1 true EP1031637A1 (fr) 2000-08-30
EP1031637B1 EP1031637B1 (fr) 2002-01-09

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US (1) US6410153B1 (fr)
EP (1) EP1031637B1 (fr)
DE (1) DE60000053T2 (fr)
GB (1) GB9903988D0 (fr)

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DE10118541A1 (de) * 2001-04-14 2002-10-17 Alstom Switzerland Ltd Verfahren zur Abschätzung der Lebensdauer von Wärmedämmschichten
US7208230B2 (en) 2003-08-29 2007-04-24 General Electric Company Optical reflector for reducing radiation heat transfer to hot engine parts
EP1903120A2 (fr) 2006-09-21 2008-03-26 Tyco Electronics Corporation Alliage à base de nickel contenant du cobalt et bisulfure de rhénium et procédé de son utilisation comme revêtement
WO2011119145A1 (fr) * 2010-03-23 2011-09-29 Siemens Aktiengesellschaft Couche d'accrochage ou alliage métallique ayant une température de transition γ/γ' élevée et un composant
EP2216420A3 (fr) * 2009-02-05 2012-06-13 Honeywell International Inc. Superalliages à base de nickel
US9752970B2 (en) 2014-04-23 2017-09-05 Rolls-Royce Plc Method of testing the oxidation resistance of an alloy
US11686208B2 (en) 2020-02-06 2023-06-27 Rolls-Royce Corporation Abrasive coating for high-temperature mechanical systems

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US6485844B1 (en) * 2000-04-04 2002-11-26 Honeywell International, Inc. Thermal barrier coating having a thin, high strength bond coat
US6939508B2 (en) * 2002-10-24 2005-09-06 The Boeing Company Method of manufacturing net-shaped bimetallic parts
SE528807C2 (sv) * 2004-12-23 2007-02-20 Siemens Ag Komponent av en superlegering innehållande palladium för användning i en högtemperaturomgivning samt användning av palladium för motstånd mot väteförsprödning
US7824606B2 (en) 2006-09-21 2010-11-02 Honeywell International Inc. Nickel-based alloys and articles made therefrom
DE102010038077B4 (de) * 2010-10-08 2018-05-30 Msm Krystall Gbr (Vertretungsberechtigte Gesellschafter: Dr. Rainer Schneider, 12165 Berlin; Arno Mecklenburg, 10999 Berlin) Wendeschneidplatte und Verfahren zu deren Herstellung
US20160214350A1 (en) 2012-08-20 2016-07-28 Pratt & Whitney Canada Corp. Oxidation-Resistant Coated Superalloy
US11674212B2 (en) * 2014-03-28 2023-06-13 Kubota Corporation Cast product having alumina barrier layer
US10577948B2 (en) * 2015-10-29 2020-03-03 MTU Aero Engines AG Turbine blade and aircraft engine comprising same

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US5366695A (en) * 1992-06-29 1994-11-22 Cannon-Muskegon Corporation Single crystal nickel-based superalloy
EP0687741A1 (fr) * 1994-06-16 1995-12-20 Csir Alliage
WO1997048827A1 (fr) * 1996-06-17 1997-12-24 Abb Research Ltd. Superalliage a base de nickel
EP0848071A1 (fr) * 1996-12-11 1998-06-17 United Technologies Corporation Compositions de superalliages

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DE10118541A1 (de) * 2001-04-14 2002-10-17 Alstom Switzerland Ltd Verfahren zur Abschätzung der Lebensdauer von Wärmedämmschichten
US6681639B2 (en) 2001-04-14 2004-01-27 Alstom (Switzerland) Ltd. Method of estimating the lifetime of thermal barrier coatings
US7208230B2 (en) 2003-08-29 2007-04-24 General Electric Company Optical reflector for reducing radiation heat transfer to hot engine parts
US8691678B2 (en) 2006-09-21 2014-04-08 Tyco Electronics Corporation Composition and method for alloy having improved stress relaxation resistance
EP1903120A3 (fr) * 2006-09-21 2008-05-07 Tyco Electronics Corporation Alliage à base de nickel contenant du cobalt et bisulfure de rhénium et procédé de son utilisation comme revêtement
US8388890B2 (en) 2006-09-21 2013-03-05 Tyco Electronics Corporation Composition and method for applying an alloy having improved stress relaxation resistance
EP1903120A2 (fr) 2006-09-21 2008-03-26 Tyco Electronics Corporation Alliage à base de nickel contenant du cobalt et bisulfure de rhénium et procédé de son utilisation comme revêtement
EP2216420A3 (fr) * 2009-02-05 2012-06-13 Honeywell International Inc. Superalliages à base de nickel
US8216509B2 (en) 2009-02-05 2012-07-10 Honeywell International Inc. Nickel-base superalloys
WO2011119145A1 (fr) * 2010-03-23 2011-09-29 Siemens Aktiengesellschaft Couche d'accrochage ou alliage métallique ayant une température de transition γ/γ' élevée et un composant
US9133345B2 (en) 2010-03-23 2015-09-15 Siemens Aktiengesellschaft Metallic bondcoat or alloy with a high gamma/gamma' transition temperature and a component
US9752970B2 (en) 2014-04-23 2017-09-05 Rolls-Royce Plc Method of testing the oxidation resistance of an alloy
US11686208B2 (en) 2020-02-06 2023-06-27 Rolls-Royce Corporation Abrasive coating for high-temperature mechanical systems

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DE60000053D1 (de) 2002-02-28
US6410153B1 (en) 2002-06-25
DE60000053T2 (de) 2002-11-14
EP1031637B1 (fr) 2002-01-09
GB9903988D0 (en) 1999-10-20

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